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RG 12A-1.8/9.0 AIRFOIL (rg12a189-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: RG 12A-1.8/9.0 AIRFOIL (rg12a189-il)
Reynolds number: 500,000
Max Cl/Cd: 86.7 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rg12a189-il-500000.txt
Download as CSV file: xf-rg12a189-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RG 12A-1.8/9.0 AIRFOIL                          
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4906   0.08437   0.08212  -0.0275   1.0000   0.0175
  -8.750  -0.4953   0.08008   0.07788  -0.0295   1.0000   0.0178
  -8.500  -0.5034   0.07554   0.07338  -0.0317   1.0000   0.0178
  -8.250  -0.5200   0.07084   0.06874  -0.0346   1.0000   0.0177
  -8.000  -0.5353   0.06579   0.06367  -0.0371   1.0000   0.0176
  -7.750  -0.5442   0.06099   0.05880  -0.0382   1.0000   0.0178
  -7.500  -0.5504   0.05633   0.05404  -0.0382   1.0000   0.0182
  -7.250  -0.5532   0.05183   0.04941  -0.0376   1.0000   0.0187
  -7.000  -0.5430   0.04848   0.04574  -0.0362   1.0000   0.0205
  -6.750  -0.5408   0.04551   0.04250  -0.0343   1.0000   0.0207
  -5.500  -0.4565   0.02093   0.01577  -0.0341   0.9942   0.0145
  -5.250  -0.4275   0.01740   0.01190  -0.0347   0.9920   0.0132
  -5.000  -0.3949   0.01547   0.00970  -0.0356   0.9895   0.0131
  -4.750  -0.3606   0.01414   0.00819  -0.0369   0.9871   0.0135
  -4.500  -0.3241   0.01339   0.00733  -0.0387   0.9849   0.0142
  -4.250  -0.2892   0.01184   0.00564  -0.0404   0.9833   0.0157
  -4.000  -0.2582   0.01137   0.00517  -0.0412   0.9783   0.0187
  -3.750  -0.2226   0.01083   0.00457  -0.0428   0.9747   0.0207
  -3.500  -0.1856   0.01000   0.00373  -0.0447   0.9722   0.0344
  -3.250  -0.1495   0.00932   0.00333  -0.0467   0.9693   0.0976
  -3.000  -0.1189   0.00878   0.00306  -0.0476   0.9632   0.1648
  -2.750  -0.0832   0.00806   0.00280  -0.0497   0.9598   0.2868
  -2.500  -0.0474   0.00702   0.00254  -0.0521   0.9573   0.4973
  -2.250  -0.0212   0.00630   0.00247  -0.0517   0.9498   0.6805
  -2.000   0.0148   0.00612   0.00238  -0.0531   0.9454   0.7380
  -1.750   0.0466   0.00601   0.00227  -0.0537   0.9377   0.7635
  -1.500   0.0813   0.00591   0.00217  -0.0548   0.9307   0.7888
  -1.250   0.1118   0.00584   0.00211  -0.0549   0.9195   0.8077
  -1.000   0.1436   0.00578   0.00203  -0.0555   0.9072   0.8208
  -0.750   0.1743   0.00576   0.00195  -0.0557   0.8925   0.8329
  -0.500   0.2037   0.00576   0.00189  -0.0557   0.8754   0.8441
  -0.250   0.2309   0.00577   0.00187  -0.0552   0.8559   0.8536
   0.000   0.2575   0.00582   0.00184  -0.0546   0.8344   0.8628
   0.250   0.2835   0.00589   0.00182  -0.0539   0.8118   0.8724
   0.500   0.3081   0.00596   0.00182  -0.0529   0.7887   0.8811
   0.750   0.3325   0.00604   0.00183  -0.0519   0.7646   0.8905
   1.250   0.3792   0.00623   0.00187  -0.0494   0.7175   0.9102
   1.500   0.4030   0.00631   0.00189  -0.0484   0.6939   0.9184
   1.750   0.4270   0.00641   0.00192  -0.0474   0.6707   0.9260
   2.250   0.4751   0.00661   0.00199  -0.0456   0.6235   0.9408
   2.500   0.4996   0.00671   0.00203  -0.0448   0.5997   0.9486
   2.750   0.5246   0.00684   0.00208  -0.0442   0.5746   0.9579
   3.000   0.5530   0.00699   0.00215  -0.0443   0.5476   0.9666
   3.250   0.5842   0.00716   0.00226  -0.0451   0.5193   0.9747
   3.500   0.6172   0.00736   0.00237  -0.0464   0.4888   0.9835
   3.750   0.6523   0.00760   0.00250  -0.0482   0.4553   0.9916
   4.000   0.6831   0.00788   0.00265  -0.0492   0.4195   1.0000
   4.250   0.7057   0.00814   0.00282  -0.0485   0.3905   1.0000
   4.500   0.7298   0.00846   0.00301  -0.0480   0.3539   1.0000
   4.750   0.7538   0.00886   0.00323  -0.0475   0.3116   1.0000
   5.000   0.7781   0.00926   0.00348  -0.0471   0.2738   1.0000
   5.250   0.8016   0.00975   0.00378  -0.0466   0.2293   1.0000
   5.500   0.8252   0.01025   0.00411  -0.0461   0.1894   1.0000
   5.750   0.8487   0.01077   0.00446  -0.0455   0.1538   1.0000
   6.000   0.8722   0.01129   0.00485  -0.0450   0.1212   1.0000
   6.250   0.8950   0.01189   0.00530  -0.0443   0.0900   1.0000
   6.500   0.9162   0.01266   0.00587  -0.0435   0.0528   1.0000
   6.750   0.9365   0.01361   0.00666  -0.0423   0.0283   1.0000
   7.000   0.9592   0.01423   0.00732  -0.0415   0.0240   1.0000
   7.250   0.9786   0.01525   0.00844  -0.0400   0.0209   1.0000
   7.500   1.0007   0.01588   0.00916  -0.0391   0.0201   1.0000
   7.750   1.0222   0.01657   0.00996  -0.0381   0.0189   1.0000
   8.000   1.0432   0.01728   0.01074  -0.0371   0.0175   1.0000
   8.250   1.0627   0.01814   0.01168  -0.0359   0.0165   1.0000
   8.500   1.0799   0.01928   0.01290  -0.0343   0.0156   1.0000
   8.750   1.0918   0.02120   0.01497  -0.0320   0.0147   1.0000
   9.000   1.1077   0.02278   0.01670  -0.0304   0.0140   1.0000
   9.250   1.1276   0.02352   0.01756  -0.0293   0.0133   1.0000
   9.500   1.1448   0.02473   0.01891  -0.0279   0.0126   1.0000
   9.750   1.1610   0.02602   0.02034  -0.0264   0.0119   1.0000
  10.000   1.1755   0.02750   0.02198  -0.0248   0.0114   1.0000
  10.250   1.1885   0.02897   0.02359  -0.0230   0.0109   1.0000
  10.500   1.1990   0.03059   0.02531  -0.0211   0.0104   1.0000
  10.750   1.2041   0.03288   0.02778  -0.0186   0.0101   1.0000
  11.000   1.1951   0.03730   0.03254  -0.0149   0.0097   1.0000
  11.250   1.1852   0.03996   0.03549  -0.0111   0.0094   1.0000
  11.500   1.1813   0.04193   0.03765  -0.0083   0.0093   1.0000
  11.750   1.1792   0.04356   0.03947  -0.0062   0.0090   1.0000
  12.000   1.1749   0.04578   0.04187  -0.0047   0.0086   1.0000
  12.250   1.1638   0.04916   0.04546  -0.0037   0.0085   1.0000
  12.500   1.1500   0.05320   0.04972  -0.0037   0.0085   1.0000
  12.750   1.1330   0.05817   0.05489  -0.0048   0.0085   1.0000
  13.000   1.1124   0.06429   0.06123  -0.0073   0.0086   1.0000
  13.250   1.0987   0.06988   0.06699  -0.0104   0.0084   1.0000
  13.500   1.0746   0.07804   0.07533  -0.0153   0.0087   1.0000
  13.750   1.0528   0.08659   0.08404  -0.0210   0.0087   1.0000
  14.000   1.0334   0.09543   0.09303  -0.0269   0.0088   1.0000
  14.250   1.0059   0.10682   0.10455  -0.0343   0.0091   1.0000
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